US10119547B2 - Housing device for a compressor stage of a compressor device that is embodied with multiple stages and method for manufacturing a housing device - Google Patents

Housing device for a compressor stage of a compressor device that is embodied with multiple stages and method for manufacturing a housing device Download PDF

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Publication number
US10119547B2
US10119547B2 US14/960,868 US201514960868A US10119547B2 US 10119547 B2 US10119547 B2 US 10119547B2 US 201514960868 A US201514960868 A US 201514960868A US 10119547 B2 US10119547 B2 US 10119547B2
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United States
Prior art keywords
area
housing device
rotor
housing
compressor
Prior art date
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Expired - Fee Related, expires
Application number
US14/960,868
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English (en)
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US20160186762A1 (en
Inventor
Marco RAUTENSTRAUCH
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Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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Assigned to ROLLS-ROYCE DEUTSCHLAND LTD & CO KG reassignment ROLLS-ROYCE DEUTSCHLAND LTD & CO KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Rautenstrauch, Marco
Publication of US20160186762A1 publication Critical patent/US20160186762A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/022—Multi-stage pumps with concentric rows of vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/54—Building or constructing in particular ways by sheet metal manufacturing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y02T50/671—

Definitions

  • the invention relates to a housing device for a compressor stage of a compressor device of an aircraft engine that is embodied in a multi-stage design in accordance with the type disclosed herein and to a method for manufacturing such a housing device in accordance with the type disclosed herein.
  • Such a compressor device has a compressor housing in which rotor blades of rotor appliances and guide blades of stator appliances are mounted.
  • the compressor housing which is adjoining the rotor blades in an exterior circumferential area is embodied with multiple housing appliances that are adjoining each other, wherein one housing appliance is respectively allocated to one compressor stage.
  • the housing appliances of the compressor device are embodied so as to be substantially identical in construction and respectively have a flange area, via which housing appliances that are adjacent to each other in the axial direction of the compressor device are connected to each other. Further, the housing appliances are embodied with a rotor area that is provided with a running-in layer and that is arranged in a radially interior cross-sectional area of the housing appliance and acts together with the rotor blades of a rotor device during operation of the aircraft engine.
  • the present invention is based on the objective to provide a housing device that can be manufactured in a simple and cost-effective manner. Further, it is an objective of the present invention to provide a simple and cost-effective method for manufacturing such a housing device.
  • the manufacture of a housing device with a small wall thickness by using metal-cutting methods is work-intensive or only possible up to a defined, possibly undesirably high minimal wall thickness.
  • the housing device is formed by a single sheet metal part.
  • the housing device according to the invention is preferably embodied for acting together with exactly one rotor device that comprises rotor blades as well as one or two stator device[s] that comprise guide blades.
  • the housing device can be manufactured in a more simple and cost-effective manner with a low self-weight and so as to be adjustable to the respectively present load case, since the respective part of the housing device can be manufactured by means of the forming process in just a few processing steps.
  • a housing device that is manufactured with the method according to the invention advantageously requires either no cutting methods or requires them only to a small extent.
  • the at least one part of the housing device is manufactured by means of a forming process that yields a shape that is close to the final dimensions, a so-called near-net shape forming process.
  • the manufacture of the respective part of the housing device can be carried out in a particularly cost-effective and simple manner, as the respective part can be manufactured in a particularly low number of processing steps.
  • shear forming methods, hydro forming methods and/or roll forming methods are possible.
  • At least one part of the housing device is preferably made of a sheet metal part or a flat base body, wherein initially the cross section or the profile of the part is manufactured and the resulting intermediate product is subsequently converted into a ring shape, with its end areas subsequently being connected to each other, preferably in a firmly bonded manner.
  • FIG. 4 shows a rendering of a second embodiment of the housing device according to the invention that corresponds to FIG. 3 ;
  • stator devices 12 are arranged at an exterior housing 16 that surrounds the interior housing 14 in the radial direction and that separates the bypass channel 2 from the engine core 5 .
  • the guide blades 13 of the stator devices 12 and the exterior housing 16 are arranged in a torque-proof manner at the engine 1 .
  • the interior housing 14 and the exterior housing 16 limit the engine core 5 in the radial direction, wherein the interior housing 14 forms an interior limitation of an air volume stream that flows through the engine core 5 , and the exterior housing 16 forms an exterior limitation of the air volume stream that flows through the engine core 5 .
  • the housing device 18 A has only one reception area 20 A or 20 B for the guide blades 13 that will be described in more detail in the following.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US14/960,868 2014-12-29 2015-12-07 Housing device for a compressor stage of a compressor device that is embodied with multiple stages and method for manufacturing a housing device Expired - Fee Related US10119547B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102014119673.2 2014-12-29
DE102014119673.2A DE102014119673A1 (de) 2014-12-29 2014-12-29 Gehäusevorrichtung für eine Verdichterstufe einer mehrstufig ausgeführten Verdichtervorrichtung und Verfahren zur Herstellung einer Gehäusevorrichtung
DE102014119673 2014-12-29

Publications (2)

Publication Number Publication Date
US20160186762A1 US20160186762A1 (en) 2016-06-30
US10119547B2 true US10119547B2 (en) 2018-11-06

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US14/960,868 Expired - Fee Related US10119547B2 (en) 2014-12-29 2015-12-07 Housing device for a compressor stage of a compressor device that is embodied with multiple stages and method for manufacturing a housing device

Country Status (3)

Country Link
US (1) US10119547B2 (de)
EP (1) EP3040560B1 (de)
DE (1) DE102014119673A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10344774B2 (en) * 2015-09-29 2019-07-09 Rolls-Royce Plc Casing for a gas turbine engine and a method of manufacturing such a casing
US10385730B2 (en) * 2014-12-10 2019-08-20 Rolls-Royce Corporation Stiffening rib
US20220251968A1 (en) * 2021-02-09 2022-08-11 General Electric Company Stator apparatus for a gas turbine engine

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6759044B2 (ja) 2016-10-11 2020-09-23 キヤノン株式会社 画像読取装置、及び画像形成装置
JP6821377B2 (ja) 2016-10-11 2021-01-27 キヤノン株式会社 画像読取装置、及び画像形成装置
JP6849378B2 (ja) * 2016-10-11 2021-03-24 キヤノン株式会社 画像読取装置、及び画像形成装置
US10542168B2 (en) 2016-10-11 2020-01-21 Canon Kabushiki Kaisha Image reading device and image forming apparatus
JP6821378B2 (ja) 2016-10-11 2021-01-27 キヤノン株式会社 画像読取装置、及び画像形成装置
JP6838922B2 (ja) 2016-10-11 2021-03-03 キヤノン株式会社 画像読取装置、及び画像形成装置
US10598046B2 (en) 2018-07-11 2020-03-24 United Technologies Corporation Support straps and method of assembly for gas turbine engine
US11215075B2 (en) * 2019-11-19 2022-01-04 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2763462A (en) 1950-01-11 1956-09-18 Gen Motors Corp Turbine casing construction
US2772856A (en) 1950-08-01 1956-12-04 Rolls Royce Structural elements for turbo-machines such as compressors or turbines of gasturbineengines
US2994508A (en) 1958-03-04 1961-08-01 Curtiss Wright Corp Lightweight compressor housing construction
US3319930A (en) 1961-12-19 1967-05-16 Gen Electric Stator assembly for turbomachines
US3338508A (en) 1965-08-23 1967-08-29 Gen Motors Corp Axial-flow compressor
US4796423A (en) * 1983-12-19 1989-01-10 General Electric Company Sheet metal panel
US5462403A (en) 1994-03-21 1995-10-31 United Technologies Corporation Compressor stator vane assembly
US20050042077A1 (en) * 2002-10-23 2005-02-24 Eugene Gekht Sheet metal turbine or compressor static shroud
US20090047126A1 (en) 2006-12-29 2009-02-19 Ress Jr Robert A Integrated compressor vane casing
US20110008165A1 (en) 2008-12-30 2011-01-13 Nathan Wesley Ottow Engine case system for a gas turbine engine
US20130177400A1 (en) 2012-01-05 2013-07-11 Mark David Ring Stator vane integrated attachment liner and spring damper
US20130259664A1 (en) * 2012-03-27 2013-10-03 David Denis Structural case for aircraft gas turbine engine
US20150159554A1 (en) 2013-05-16 2015-06-11 Snecma Aircraft turbofan comprising an intermediate ring with simplified downstream support

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2763462A (en) 1950-01-11 1956-09-18 Gen Motors Corp Turbine casing construction
US2772856A (en) 1950-08-01 1956-12-04 Rolls Royce Structural elements for turbo-machines such as compressors or turbines of gasturbineengines
US2994508A (en) 1958-03-04 1961-08-01 Curtiss Wright Corp Lightweight compressor housing construction
US3319930A (en) 1961-12-19 1967-05-16 Gen Electric Stator assembly for turbomachines
US3338508A (en) 1965-08-23 1967-08-29 Gen Motors Corp Axial-flow compressor
US4796423A (en) * 1983-12-19 1989-01-10 General Electric Company Sheet metal panel
US5462403A (en) 1994-03-21 1995-10-31 United Technologies Corporation Compressor stator vane assembly
US20050042077A1 (en) * 2002-10-23 2005-02-24 Eugene Gekht Sheet metal turbine or compressor static shroud
US20090047126A1 (en) 2006-12-29 2009-02-19 Ress Jr Robert A Integrated compressor vane casing
US20110008165A1 (en) 2008-12-30 2011-01-13 Nathan Wesley Ottow Engine case system for a gas turbine engine
US20130177400A1 (en) 2012-01-05 2013-07-11 Mark David Ring Stator vane integrated attachment liner and spring damper
US20130259664A1 (en) * 2012-03-27 2013-10-03 David Denis Structural case for aircraft gas turbine engine
US20150159554A1 (en) 2013-05-16 2015-06-11 Snecma Aircraft turbofan comprising an intermediate ring with simplified downstream support

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
European Search Report dated May 23, 2016 for counterpart European Application No. 15197335.1.
German Search Report dated Oct. 28, 2015 for related German Application No. DE 10 2014 119 673.2.

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10385730B2 (en) * 2014-12-10 2019-08-20 Rolls-Royce Corporation Stiffening rib
US10344774B2 (en) * 2015-09-29 2019-07-09 Rolls-Royce Plc Casing for a gas turbine engine and a method of manufacturing such a casing
US20220251968A1 (en) * 2021-02-09 2022-08-11 General Electric Company Stator apparatus for a gas turbine engine
US11512611B2 (en) * 2021-02-09 2022-11-29 General Electric Company Stator apparatus for a gas turbine engine
US20230044297A1 (en) * 2021-02-09 2023-02-09 General Electric Company Stator apparatus for a gas turbine engine

Also Published As

Publication number Publication date
EP3040560B1 (de) 2018-04-25
EP3040560A1 (de) 2016-07-06
DE102014119673A1 (de) 2016-06-30
US20160186762A1 (en) 2016-06-30

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